Aircraft structures are subjected to numerous environments that cause external and internal loads to vary. Calculating such loads is an essential part of aircraft development and safety, but requires a complex combination of tools and methods. Watch our webinar series and learn how CAE software can be better used to improve loads methods and processes. …
The lifecycle cost and reliability of flight control surfaces are critical aspects of fixed wing aircraft development. Physical prototype testing is used to validate and improve the performance of common control surfaces such as ailerons, elevators, rudders, spoilers, flaps, slats, and air brakes. Unfortunately such flight control systems have large loads that are difficult and …
The JEC Group awarded Digimat with its 2014 JEC Americas Innovation Award at its recent event in Boston. JEC awards have showcased excellence in composite manufacturing for 14 years, singling out more than 150 companies and 350 partners for contributions to improving composites technology and enhancing value for end users. Digimat, the nonlinear, multi-scale material and structure …
Below are a list of OS and hardware requirements necessary for MSC Nastran Desktop 2014. Microsoft Windows Requirements Hardware Platforms Intel EM64T Operating System Microsoft Windows 7 Professional SP1 (64bit only) Compiler Versions Microsoft Visual Studio 2012 11.0.61030 Update 4 Fortran Composer XE 2013.2.146 for Windows, Intel Fortran Version 13.1.0.146† Other 3 Button Mouse NTFS …
Question: What are some of the optimization capabilities in MSC Nastran? Answer: Just to name a few: Size Shape Topometry Topology Multi Model Optimization Brief descriptions of each are given below. SIZE Use size optimization to improve the performance of designs by varying basic design parameters such as beam cross sectional dimensions, sheet thicknesses, composite …
Failure of continuous fiber composites are much more complex than metal. Continuous fiber structure involves most of the time stacking of several plies, each ply being characterized by a single fiber orientation. The intra-laminar failure mechanism is mainly due to delamination, while the inter-laminar failure is governed by various mechanisms like matrix cracking, fiber breakage …
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